Results
2012-21-16: We are adopting a new airworthiness directive (AD) for certain BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by hydraulic pipe ruptures in the center of the cabin resulting in passengers being contaminated with hydraulic fluid. This AD requires installing a hydraulic fluid containment system. We are issuing this AD to prevent harmful or hazardous concentrations of hydraulic fluid or hydraulic vapor from entering the passenger compartment, possibly resulting in injury to the passengers.
2012-21-17: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-214 and -232 airplanes. This AD was prompted by reports that medium-head fasteners were installed in lieu of shear-head fasteners on a certain upper panel, which manufacturer fatigue and damage tolerance analyses demonstrated could have an effect on panel fatigue life. This AD requires repetitive inspections for cracking of certain fasteners, and repairs if necessary. We are issuing this AD to detect and correct such cracking, which could result in the loss of structural integrity of the airplane.
2012-21-18: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model MD-90-30 airplanes. This AD was prompted by reports of fatigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. This AD requires repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not supporting the limit load condition, which could lead to loss of the structural integrity of the wing.
48-28-01: 48-28-01 TEMCO: Applies to All Models GC-1A and GC-1B Aircraft. I. Inspection required at each 20 hours operation until compliance with item II is made. Cracks are occurring in the last bulkhead (Station 185) of the fuselage at the bottom rudder hinge and stop fitting, and the bulkhead must be inspected for such cracks. If cracks are found, a repair must be made in accordance with item II. II. Compliance required not later than September 1, 1948. To preclude the possibility of a structural failure in the rear bulkhead of the fuselage, at the bottom rudder hinge and stop, a steel reinforcement must be made as follows: 1. If cracks are found in the bulkhead drill No. 50 (0.07 diameter) check holes at end of each crack. 2. Fabricate and install a steel reinforcement fitting as defined in TEMCO Drawing 11-213-5074. The Texas Engineering and Manufacturing Co., Inc., will furnish free of charge the steel reinforcement fitting described in item 2. (TEMCO Customer Service Maintenance Bulletin No. 26 covers this same subject.)
47-10-31: 47-10-31 LOCKHEED: (Was Service Note 1 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. At periods not to exceed 100 hours the webs of all landing gear torque arms should be examined closely at the knee bolt ends for the presence of cracks. When a nose gear arm is found to be cracked, it should be replaced with a new part. When either main gear arm is found to be cracked, the 283557 or 292132 aluminum alloy torque link assemblies on both main gears should be replaced with 293882 steel torque link assemblies. When Note 47-10-21 is complied with, this periodic inspection procedure for the main gear may be discontinued.
67-01-02: 67-01-02 GENERAL ELECTRIC: Amendment 39-332 as amended by Amendment 39-536 and Amendment 39-1085 is further amended by Amendment 39-2688. Applies to Model CT58-100-1, CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58-140-2, T58-GE-1 and T58-GE-5 Engines. Compliance required as indicated. To ensure adequate life limit margin for first stage compressor rotor discs, remove from service G.E. P/N's 37D400218P101, 37D400218P101 CEB #148, 37D400218P102, 37D400359P101, 37D400359P102, 3920T11P01, 3920T11P02, 5013T06P01, 5001T20P01, and 5001T20P02 as follows: (a) Discs with more than 9,700 cycles on October 15, 1970, prior to the accumulation of 200 additional cycles. (b) Discs with 9,700 cycles or less on October 15, 1970, before 9,900 cycles. For the purposes of this AD a cycle is considered as any engine operating sequence involving engine start, at least one acceleration to a power required for take off, and shutdown. Amendment 39-332 became effective December 29, 1966. Amendment 39-536 became effective January 9, 1968. Amendment 39-1085 became effective October 15, 1970. This amendment 39-2688 becomes effective August 24, 1976.
2012-21-19: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 freighter series airplanes; Model A330-200 and - 300 [[Page 65813]] series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports of ram air turbine (RAT) pump failure. This AD requires inspecting the RAT pump anti-stall valve for correct setting, re-identifying the RAT pump, performing a functional ground test of the RAT, and replacing the RAT pump or the RAT assembly with a serviceable part if necessary. We are issuing this AD to detect and correct malfunction of the RAT pump, which could lead to in-flight loss of the RAT-pump pressurization, possibly resulting in reduced control of the airplane.
2012-21-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of deformation at the neck of the pressure regulator body on the oxygen cylinder and regulator assemblies (CRAs), and an electrical wiring harness in the area of the oxygen cylinder with no protective conduit sleeving. This AD requires inspecting to determine if certain oxygen pressure regulators are installed and replacing oxygen CRAs containing pressure regulators that do not meet the required material properties. This AD also requires inspecting for damaged wiring, and repairing or replacing wiring if necessary. We are issuing this AD to prevent rupture of the oxygen cylinder, which in the case of cabin depressurization, would lead to oxygen not being available when required; and to detect and correct unprotected wiring that could chafe against the oxygen system components or surrounding structure in the area, and lead to electrical arcing and an oxygen-fed fire.
69-17-03: 69-17-03 GENERAL ELECTRIC: Amdt. 39-824. Applies to General Electric Models CT58-100-1, CT58- 100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58-140-2, T58-GE-1 and T58-GE-5 engines, installed in Boeing Vertol 107 and Sikorsky S61 and S62 aircraft. To prevent failures of first and second stage turbine rotor discs remove from service General Electric part numbers listed below with more than 10,100 cycles at the time of receipt of this telegram, unless already accomplished. STAGE 1 DISCS STAGE 2 DISCS 278D978P002 278D979P002 37D400498P101 37D400499P101 37D400010P101 37D400004P102 37D400227P101 37D400228P102 37D400307P101 4002T96P01 4002T17P01 For the purposes of this airworthiness directive a cycle is considered as any engine operating sequence involving engine start, at least one acceleration to a power required for takeoff and shutdown. Since it was found that immediate corrective action was required, notice and public procedure thereon was impracticable and contrary to the public interest and good cause existed for making the airworthiness directive effective immediately as to all known U.S. operators of Boeing Vertol 107 and Sikorsky S61 and S62 aircraft with General Electric Engine Models CT58-100-1, CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58- 140-2, T58-GE-1 and T58-GE-5, by individual telegrams dated August 12, 1969. These conditions still exist and the airworthiness directive is hereby published in the FEDERAL REGISTER as an amendment to Section 39.13 of Part 39 of the Federal Aviation Regulations to make it effective as to all persons. This amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated August 12, 1969.
76-03-07: 76-03-07 BEECH: Amendment 39-2515. Applies to Models 200 and A100-1 (Serial Numbers BB-2 through BB-58) airplanes. Compliance: Required as indicated, unless already accomplished. To preclude loss of rudder control, within the next 50 hours' time in service after the effective date of this AD, accomplish the following: A) Inspect the P/N 101-524062-1 aft rudder push rod assembly for loose rivets securing the adapters to the aluminum tube in accordance with Beechcraft Service Instruction 0778-153, dated January, 1976, or later approved revisions. Replace any aft rudder push rod assembly having this condition with airworthy P/N 101-524062-1 aft rudder push rod assembly or P/N 101-524265-1 aft rudder push rod assembly. B) If a loose rivet or other defect is found as a result of the inspection required herein provide the FAA with written notification thereof utilizing Malfunction and Defect Report (FAA Form 8330-2) describing the condition and giving the total operating time on the airplane or part at the time of discovery (Reporting approved by the Office Management and Budget under OMB No. 04-R0174). C) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective February 20, 1976.
93-10-07: 93-10-07 TEXTRON LYCOMING: Amendment 39-8587. Docket 91-ANE-53. Applicability: Textron Lycoming ALF502R and ALF502L series turbofan engines installed on but not limited to British Aerospace BAe-146 and Canadair Challenger CL-600 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent corrosion and cracking of the third stage compressor disks, that could result in engine failure, accomplish the following: (a) Repair and mark, or replace, third stage compressor disks, Part Number (P/N) 2-101-263-02, P/N 2-101-263-05, P/N 2-101-263-09, P/N 2-101-263-R10, or third stage disk assemblies P/N 2-101-630-04, P/N 2-101-630-05, P/N 2-101-630-08; at the next part exposure, after the effective date of this AD, but no later than, 7,500 cycles since new, in accordance with Textron Lycoming Service Bulletin No. ALF502R 72-259, dated August 13, 1991, or Service Bulletin No. ALF502L 72-259, dated August 13, 1991, as applicable. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The repairing and marking, or replacement shall be done in accordance with the following Textron Lycoming service bulletins: Document No. Pages Date ALF502R 72-259 1-5 August 13, 1991 Total pages: 5 ALF502L 72-259 1-5 August 13, 1991 Total Pages: 5 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Textron Lycoming, Stratford Division, 550 Main Street, Stratford, CT 06497-7593. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (e) This amendment becomes effective on August 10, 1993.
47-21-11: 47-21-11 REPUBLIC: (Was Mandatory Note 1 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 5 to 174, Inclusive. Compliance required prior to July 1, 1947. In order to prevent short circuiting of terminal studs on the firewall, remove each stud, enlarge the hole (0.316 drill) and insert a bushing (P/N 17F82080-1). (Republic Seabee Service Bulletin No. 1, dated December 18, 1946, covers this same subject.)
2012-21-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD- 83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of fatigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. This AD requires repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not supporting the limit load condition, which could lead to loss of structural integrity of the wing.
2012-21-07: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109S helicopters to require modifying the electrical power distribution system to carry a higher electrical load. This AD was prompted by an electrical failure on an Agusta Model A109E helicopter that resulted from ``inadequate functioning of the 35 amperes (amps) BATT BUS circuit breaker.'' The actions of this AD are intended to require modifying the electrical power distribution system to prevent failure of the circuit breaker, loss of electrical power to instruments powered by the ``BATT BUS'' system, and subsequent loss of control of the helicopter.
75-17-11: 75-17-11 ALEXANDER SCHLEICHER: Amendment 39-2313. Applies to ASW 15 gliders, serial numbers 15001 thru 15183, certificated in all categories. Compliance is required within the next ten hours time in service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time in service from the last inspection until the rudder nose is reinforced in accordance with paragraph (b)(2) of this AD. To prevent rudder jam due to improper fin-rudder nose clearance, accomplish the following: (a) Visually inspect the rudder nose for deformation and measure the gap between the fin and rudder. The acceptable gap is between 2 to 3 mm at the lower rudder hinge tapering to an allowable gap of between 1 to 2 mm at the upper end of the vertical fin. (b) If the measured gap is not within limits, or a deformation of the rudder nose is found, comply with the following: (1) Reform the rudder nose inward until the gap is within limits by applying heat in accordance with paragraph 1 of the instructions contained in Alexander Schleicher ASW 15 Technical Note 10 dated January 30, 1973, or an FAA-approved equivalent. (2) Reinforce rudder nose in accordance with paragraph 2 of the instructions contained in Alexander Schleicher ASW 15 Technical Note 10 dated January 30, 1973 and Alexander Schleicher drawing L-272 150.36/37.B1.33, or an FAA-approved equivalent. This amendment becomes effective August 18, 1975.
2012-21-05: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model G58 airplanes. This AD was prompted by notification from Hawker Beechcraft Corporation that certain affected aircraft were produced with the incorrect gauge wiring installed. This AD requires replacement of the incorrect gauge wiring with the correct wiring required by type design and the aircraft's circuit protection. We are issuing this AD to correct the unsafe condition on these products.
2012-21-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD was prompted by reports of two in-service occurrences on Model 737-400 airplanes of total loss of boost pump pressure of the fuel feed system, followed by loss of fuel system suction feed capability on one engine, and in-flight shutdown of the engine. This AD requires repetitive operational tests, and corrective actions if necessary. We are issuing this AD to detect and correct loss of the engine fuel suction feed capability of the fuel system, which, in the event of total loss of the fuel boost pumps, could result in dual engine flameout, inability to restart the engines, and consequent forced landing of the airplane.
2012-21-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by a design review following a ground fire incident and reports of flammable fluid leaks from the wing leading edge area onto the engine exhaust area. This AD requires modification of the fluid drain path in the leading edge area of the wing. We are issuing this AD to prevent flammable fluid from leaking onto the engine exhaust nozzle, which could result in a fire.
48-21-01: 48-21-01 BELLANCA: Applies to All Aircraft Equipped With Franklin Model 6A4-150- B3 and B31 Engines. Compliance required after each 25 hours of operation. To prevent possible binding of accelerator pump linkage in Marvel-Schebler MA-3-SPA carburetor, check for worn accelerator pump linkage. Worn parts should be replaced. Marvel- Schebler have a kit (Part A666-581) available for this purpose. (Franklin Service Bulletin No. 61 covers this same subject.)
57-25-01: 57-25-01 Applies to All Aircraft engaged in Spraying Operations, Including Restricted Purpose Aircraft Certificated Under CAR Part 8 Equipped With Diaphragm Type Spray Pressure Regulators Vented in the Cockpit. Compliance required by February 1, 1958. A recent accident was caused by the failure of the diaphragm in a spray pressure regulator which permitted spray fluid to enter the cockpit through the regulator vent. Since this accident, reports have been received of several other cases of failures of these units. To prevent the release of toxic vapors into cabins or cockpits of spray planes, it is required that all diaphragm type pressure regulators be vented to the outside of the airplane. This venting may be accomplished similar to the spray tank venting noted in Section 2.415, Appendix A, of CAM 8 by means of a suitable tubing or hose extension to the outside of the fuselage.
2012-20-07: We are superseding an existing airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; and all Model A319, A320, and A321 series airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This new AD requires revising the maintenance program to incorporate revised fuel maintenance and inspection tasks, and adds airplanes to the applicability. This AD was prompted by Airbus issuing more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2000-07-11 R1: We are rescinding an airworthiness directive (AD) for all Piaggio Aero Industries S.p.A Model P-180 airplanes. That AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. We issued that AD to prevent the brake hydraulic fluid from leaking because of the brake assembly rods contacting the brake valve tubing, which could result in the inability to adequately stop the airplane during ground operations. Since we issued that AD, we have determined this is no longer an unsafe condition and that regularly scheduled annual inspections address this subject.
75-17-22: 75-17-22 SOCATA: Amendment 39-2324. Applies to Socata Models MS880B and MS885 airplanes, certificated in all categories, Serial Numbers 1 through 395 which have aluminum lateral front horizontal stabilizer attachment brackets installed. Compliance is required as indicated, unless already accomplished. To prevent failure of the aluminum lateral front horizontal stabilizer attachment brackets, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, inspect the left and right lateral front horizontal stabilizer attachment brackets for cracks in accordance with Socata Service Rallye No. 12/1, Gr. 55.01 dated January 1972 or an FAA- approved equivalent. (b) If cracks are found in either bracket, before further flight, comply with paragraph (d) of this AD. (c) If no cracks are found, within the next 100 hours' time in service after the effective date of this AD, comply with paragraph (d) of this AD. (d) Replace the left and right aluminum lateral front horizontal stabilizer attachment brackets with steel brackets, P/Ns 880.33.0.106.1 and 880.33.0.106.2, respectively. This amendment becomes effective August 19, 1975.
2012-20-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200 and -200C series airplanes. This AD was prompted by a report of elevator vibration and bearing swage failures. This AD requires, for certain airplanes, repetitive inspections for any discrepancies (such as a gap or a loose spacer) of the aft attach lugs for the elevator tab control mechanism, and replacement if necessary; and, for other airplanes, contacting the FAA for inspection or repair instructions and doing the work specified in those instructions. We are issuing this AD to detect and correct discrepancies in the aft attach lugs for the elevator tab control mechanism, which could result in elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and loss of airplane control.
96-07-05: 96-07-05 DORNIER: Amendment 39-9554. Docket 95-NM-136-AD. Applicability: Model 328-100 series airplanes, serial numbers 3005 through 3024 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously.To prevent failure of the attachment structure of the rudder damper in the event of aerodynamic gust loads, accomplish the following: (a) Within 6 months after the effective date of this AD, install a reinforcement doubler on the rudder skin in accordance with Dornier Service Bulletin SB-328-27-063, Revision 1, dated January 26, 1995. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with Dornier Service Bulletin SB-328-27-063, Revision 1, dated January 26, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on April 29, 1996.